Flying body construction



Dec. 3, 1963 Filed June 27, 1961 F. ZEYHER FLYING BODY CONSTRUCTION 2Sheets-Sheet l Inventor:

FE/TZ Z15 7/7 15? -M p-rTat/V Dec. 3, 1963 F. ZEYHER FLYING BODYCONSTRUCTION 2 Sheets-Sheet 2 Filed June 27, 1961 United States PatentOfi ice Patented ec. 3, 1963 3,112,906 FLYING RUDY CONSTRUCTION FritzZeyher, flttobrunn, near Munich, Germany, assignor toliiillrow-Entwicklungeu Kommanditgesellschaft, Postabholfach, Munich,Germany Filed June 27, 1% Ser. No. 119,970 Claims priority, applicationGermany .iuly 1, 1%0 19 Claims. (Cl. 244-138) This invention relates ingeneral to aircraft or flying body constructions and in particular to atraining head construction for a fllying body including means forslowing the descent thereof and for absorbing the impact shock uponlanding thereof.

Prior to the present invention, it was known to employ devices forabsorbing shocks for flying bodies or aircraft, such as rockets andmissiles, which include certain portions which are made to deform orbreak off in effecting the braking action on the body while it hits theground. For example, these parts are arranged so that they will beexpanded, bent, out off, buckled or chipped. Devices of this character,however, have the disadvantage that because of the permanent deformationof the parts which takes place the training head cannot be used, or itcan be used again only after a timeconsuming replacement of the deformedportions.

in some instances, devices of the above nature are supplemented byparachutes which are automatically ejected for braking the descentvelocity of the flying body, but such devices have the disadvantage thatthey are not arranged to effect descent of the body with the headportion first, but, rather, the more fragile tail portion, in manyinstances, strikes the ground first upon impact. To employ a combinationof devices of this character, it is necessary, therefore, to haveadditional shock absorbing equipment in the tail, as Well as in the headportion. When very large parachutes are employed, the bodies do notdescend rapidly enough to prevent a drifting out of the training ortarget area.

In accordance with the present invention, there is provided a flyingbody construction which includes means for attaching a training headportion. The training head portion, in accordance with the invention,comprises severable shell portions shaped as a nose cone which arehinged at their base so that the shell portions may be separated to openthe head portion when the flying body begins its descent. Arrangedwithin the shell portions are a pair of small sized parachutes havingguide line connections to support the flying body for descent with theforward or head portion downward.

In accordance with a further feature of the invention, the head portionincludes a central ground penetrating spike or rod mounted and arrangedso that a portion thereof penetrates the ground up to a predeterminedextent, at which further penetration is restricted. The spike isadvantageously mounted within a cylinder and the end of the spike isprovided with a piston head portion which lies therein to permitabsorption of the impact shock after the head portion strikes the groundand penetrates into the ground to a predetermined amount.

In a preferred arrangement, the spike member is provided with a shearingpin which holds the same in a fully extended position and which must bebroken before the piston portion thereof may slide in the cylinder. Thisshearing pin insures that the spike will penetrate into the ground forat least a small amount until a force suflicient to shear the pin isencountered. Further shock absorption is thereafter accommodated by themovement of the piston within the cylinder. The cylinder isadvantageously filled with a fluid which, in a preferred arrangement,

is displaced through small sized escape openings which are closed by acover varnish which is pushed off by the force of the displaced fluidunder the movement of the spike member. A feature of this particularprovision is that the escape openings are covered during movement of thespike to gradually reduce the discharge area for the fluid and provide auniform force action on the spike member during shock absorption.

It is an object of this invention to provide an improved flying bodyconstruction.

A further object of the invention is to provide a flying body traininghead having means for permitting a rapid descent of the flying body andfor absorbing the impact force which occurs when the flying body hits orstrikes the ground and without destruction of the parts of the flyingbody.

A further object of the invention is to provide a training headconstruction for a flying body which includes shell portions which arehingedly connected at their bases to permit separation and openingthereof and including a shock absorbing spike member mounted within saidshell portion arranged to penetrate the ground upon impact andthereafter to slide inside of a piston having fluid means for absorbingthe shock of impact.

A further object of the invention is to provide a flying body whichincludes a severable head portion havinga pair of cooperating shellmembers which are hingedly mounted at their bases permitting outwardseparable movement to open the head portion and wherein the head portionincludes a pair of parachutes having guide means for suspending thechutes from the trailing portion of the flying body, and furtherincluding fluid piston cylinder shock absorbing means with the shellmembers.

A further object of the invention is to provide a flying body havingparachutes stored in a head portion which opens at a predetermined timeduring flight and in which the parachutes are guided to suspend theflying body from the tail portion thereof, and further including shockabsorbing means within the head portion displaceable upon contact of thehead portion with the ground to absorb the shock of impact.

A further object of the invention is to provide a flying bodyconstruction which is simple in design, rugged in construction andeconomical to manufacture.

The various features of novelty which characterize the invention arepointed out with particularity in the claims annexed to and forming apart of this specification. For a better understanding of the invention,its operating advantages and specific objects attained by its use,reference should be had to the accompanying drawings and descriptivematter in which there is illustrated and described a preferredembodiment of the invention.

In the drawings:

FIG. 1 is an elevational view of a flying body having a headconstruction in accordance with the invention indicated in a positionshortly after the actuation of the descent control mechanism;

FIG. 2 is an elevational View of the flying body in FIG. 1 indicated inthe position it assumes upon contact with the ground; and

FIG. 3 is an enlarged fragmentary transverse section of the traininghead of the flying bodies indicated in FIGS. 1 and 2 with the parachutesindicated in a position stored within the head portion.

Referring to the drawings in particular, the invention embodied thereinincludes a flying body generally designated 30 having an elongated bodyportion 1 and a head portion generally designated 2 which is detachablysecured thereto.

As best seen in FIG. 3, the head portion 2 includes a cylindrical baseportion 10 having external threads 3 which engage an internal thread ofthe body portion 1. In accordance with-the invention, the training head2 includes two complementary half conical members 2a and 2b which arehingedly mounted at their lower ends or bases on hinges 4 aflixed to thecylindrical portion 10.

In the interior space between the shell portions 2a and 2b there isprovided a landing spike or element generally designated 5' having oneend which includes a piston rod portion 5a, indicated in FIG. 3 in itsextended position, in an upper sleeve portion 8, and a piston portion 11which reciprocates in a cylinder 9 mounted on the cylindrical base itThe cylinder 9 and the landing spike 5 are concentric with the axis ofthe flying body.

The spike member 5 is held in the extended position in respect to thecylinder 9 by a shearing pin 26 which permits the opposite end 51; topenetrate into the ground upon initial impact before the pin is shearedto cause reciprocation of the piston 11 within the cylinder 9 and afurther absorption of the landing impact forces.

To insure that the spike member 5 penetrates the ground only a smallextent, there is provided restriction means designated 16 which, in theembodiment indicated, is a flange which inhibits further penetration.The restriction means 16 may advantageously include spreading members ofa size chosen to achieve the desired impact force distribution andground penetration.

The interior spaces between the shell portions 2a and 2b are also filledwith parachutes 6 and '7 which retard the descent of the flying body 20after the shell portions 2:: and 2b separate to liberate the chutes.Means (not shown) are advantageously provided to insure automaticopening of the chutes in the air current. Shroud lines 13 and 14 areconnected to the parachutes and extend through openings or cars 15 whichare provided at a trailing end portion 26 of the flying body. Theshrouds 12 and 14 extend back along the flying body and are securedwithin the head portion 2 to the cylinder 9. The directing of the shroudlines in this manner prevents the flying body from turning 180 to causeit to hit the ground with its trailing or tail end 26 striking first. Inthe arrangement illustrated, the flying body will maintain its positionas shown in FIG. 2, even after the parachutes have opened. The speed ofthe flying body, due to the opening of the parachutes, is reduced to anextent which is in conformity with the strength of the landing spike 5and the associated mechanism.

The shock absorbing action of the landing spike 5 is regulated by fluidsuch as air, water or oil which is placed in the cylinder 9 and which isdisplaced through small sized opening 12 in an amount equal to a valueof kinetic energy which is the same as the kinetic energy which is to bewithdrawn from the whole aircraft or flying body. By the controlled timedependent change of the converted energy amount, it is possible that theflying body is uniformly retarded or delayed in an optimum manner.

The delaying or retarding force is produced by the fluid pressure withinthe cylinder 9. The reaction force is transferred to the piston 11 whichis slidable in the cylinder 9 and is transferred via the spike member 5to the ground. Assuming that the flying body will strike a completelyhard, unyielding surface, the initial flying body speed will be the sameas the velocity of the piston 11.

Bores 12 are closed with a cover varnish and the liquid or fluid withinthe cylinder may flow out to the bores when the lacquer or cover varnishis pushed off. Due to the path of the piston past the bores 12 duringshock absorption, the fluid exit or discharge cross section iscontinuously reduced so that the pressure within the cylinder 9 remainssubstantially constant. The velocity of the piston relative to theflying body and, thus, also the velocity of the flying body will beforced to be decreased in a desired manner.

Due to the penetration of the end 5b in the ground, the extent of delayof the retarding action is further enhanced. Further, the penetration ofthe shock absorbing point that hits the ground produces a furtheradvantage for lightweight aircraft having only a small length, bypreventing it from flipping over. When the spike 5 enters the ground itwill remain in a vertical position as indicated in FIG. 2. The spikemember 5 will not penetrate too deeply even in very soft areas, such assandy or marshy areas, because of the resistance surface 16.

In accordance with a further feature of the invention, the severablehalf conical portions 2a. and 2b are auto matically separated by theexplosion of a charge 17 in the spike member 5 which causes a cap 18 tobe dislodged which holds the severable conical portions together. Means,such as a fuse connection between the charge and the flying body engineis provided to effect detonation 0f the charge after the engine hasburned out.

The means for igniting the charge may advantageously include, forexample, a battery 35 arranged at the bottom 10 and having a time clock36 connected by means of lines 37 and 33 to the battery. An additionaligniting lead extends through the bore 39 and is connected via lines 40and 41 to an igniting member 42 located behind the charge 317. When theclock 36 runs down after being set, the time adjusted motor clock willcause ignition of the charge by a current impulse from the battery 45.

In order to prevent the parachutes from being dragged along the groundby the wind after landing, means are provided to cut the shroud lines 13and 14 after landing.

The parachute lines 13 and 14 are guided upwardly (or forwardly) alongthe sleeve element 12 and extend into the cylinder 8 and are connectedto a line-holding piston portion 32 secured to the spike S at a locationremoved from the piston 11. When the forward end of the spike contactsthe ground, the piston element 32 moves relatively to the sleeve 38 andcauses a cutting of the lines which are held in openings of the sleeveat each side of the piston. In this manner, the parachute will be freedimmediately after the device has contacted the ground.

While a specific embodiment of the invention has been shown anddescribed in detail to illustrate the application of the inventiveprinciples, it will be understood that the invention may be embodiedotherwise without departing from such principles.

What is claimed is:

1. A flying body particularly adapted for training purposes comprising abody having a head portion including a base, a plurality of shellportions hingedly connected to said base and being displaceable abouttheir hinge connection to open said head portion, a parachute enclosedin said head portion between said shell portions for slowing the descentof the flying body and connected to said body adjacent the end thereofopposite from said head to insure descent with the head portion firstwhen said body is supported by said parachute, and piston and cylindershock absorber spike means connected to said body and located withinsaid head portion including relatively displaceable piston and cylindermeans adapted to give upon contact with the ground to absorb the impactof landing.

2. A device according to claim 1, wherein the piston and cylinder meansincludes a piston spike member which is reciprocable in a cylindersecured to said base.

3. A flying body according to claim 2, wherein said piston spike memberis located within said shell portions and carries a cap holding saidshell portions together during flight.

4. A device according to claim 3, including means for causing said capto be displaced to open said shell members.

5. A flying body according to claim 1, wherein said piston and cylindershock absorber spike means includes an elongated cylinder having aplurality of openings along its length, and a spike having a pistonportion displaceable along the length of said cylinder upon contact withthe ground to expel fluid out said openings.

6. A flying body according to claim 5, wherein the openings of saidcylinder are arranged so that a substantially constant force acts onsaid piston as the fluid is displaced out said openings.

7. A flying body according to claim 1, wherein said base is connected toa tail extending rearwardly from said head in respect to the flightdirection of the flying body and said parachute includes means connectedto said tail so that said parachute supports said flying body from thetail.

8. A flying body comprising a body, a head having a base portionconnected to said body, a hollow cylinder mounted on said base portionand extending forwardly in a flight direction therefrom, a spike memberhaving a piston end portion reciprocatable in said cylinder andextending forwardly therefrom to present an end for contact with theground, said spike member being reciprocatable in said cylinder toabsorb the impact forces of the spike member hitting the ground, aplurality of shell members enclosing said spike member and said cylinderand being displaceably connected to said base, and at least oneparachute within said shell members having shroud means connected tosaid body at a location spaced rearwardly in respect to flight directionfrom said head, said shell members being openable to expose theparachute to retard the descent of the flying body.

9. A flying body according to claim 8, wherein said cylinder is providedwith a plurality of openings spaced along the length thereof.

10. A flying body according to claim 9, wherein the openings in saidcyclinder are covered with a displaceable material.

11. A flying body according to claim 8, including at least twoparachutes within said shell portions connected to said body.

12. A shock absorbing device for the braking of flying bodies bothduring their descent and after their hitting the ground comprising atrailing body portion, a training head adapted to be positioned at theforward end of said trailing body portion and having at least twodish-shaped portions, a landing spike extending forwardly in said headand positioned within said dish-shaped portions and displaceable in anaxial direction rearwardly upon impact to absorb shock, and a parachutelocated within said dish-shaped portions connected to said trailing bodyportion at a location to lower the trailing body portion and saidtraining head with said training head first.

13. A shock absorbing device according to claim 12, wherein the landingspike includes a piston portion slidable in a fluid cylinder.

14. A shock absorbing device according to claim 13, wherein said fluidcylinder includes a plurality of openings along its length arranged sothat the movement of the piston portion of said spike member is retardedin a constant manner during the entire shock absorption and brakingmovement of the flying body.

15. A shock absorbing device according to claim 13, wherein said spikeis provided with a resistance surface to prevent too deep a penetrationinto soft ground.

16. A shock absorbing device according to claim 13, including a capcovering said severable dish-shaped portions.

17. A shock absorbing device according to claim 16, including explosivecharge means for shooting off the cap to free said dish-shaped portions.

18. A shock absorbing device according to claim 12, including means forsevering the line connecting the parachute to said trailing body portionafter impact.

19. A flying body particularly adapted for training purposes, comprisinga body having a head portion, a parachute having lines connected to thetrailing end of said body to suspend the body head-first when openedduring descent of the flying body and being located in said headportion, said head portion including shell portions enclosing theparachuate constructed and arranged to separate to expose the parachute,a shock absorber including a cylinder secured to said head portion andlocated within said shell portions and a spike element including apiston portion displaceable in said cylinder and having a forwardportion adapted to penetrate the ground upon landing, said piston beingdisplaceable in said cylinder upon receiving a landing impact.

References Cited in the file of this patent UNITED STATES PATENTS1,777,188 Wiley Sept. 30, 1930 2,426,585 Bean et al. Sept. 2, 19472,713,467 Schreiber July 19, 1955

1. A FLYING BODY PARTICULARLY ADAPTED FOR TRAINING PURPOSES COMPRISING ABODY HAVING A HEAD PORTION INCLUDING A BASE, A PLURALITY OF SHELLPORTIONS HINGEDLY CONNECTED TO SAID BASE AND BEING DISPLACEABLE ABOUTTHEIR HINGE CONNECTION TO OPEN SAID HEAD PORTION, A PARACHUTE ENCLOSEDIN SAID HEAD PORTION BETWEEN SAID SHELL PORTIONS FOR SLOWING THE DESCENTOF THE FLYING BODY AND CONNECTED TO SAID BODY ADJACENT THE END THEREOFOPPOSITE FROM SAID HEAD TO INSURE DESCENT WITH THE HEAD PORTION FIRSTWHEN SAID BODY IS SUPPORTED BY SAID PARACHUTE, AND PISTON AND CYLINDERSHOCK ABSORBER SPIKE MEANS CONNECTED TO SAID BODY AND LOCATED WITHINSAID HEAD PORTION INCLUDING RELATIVELY DISPLACEABLE PISTON AND CYLINDERMEANS ADAPTED TO GIVE UPON CONTACT WITH THE GROUND TO ABSORB THE IMPACTOF LANDING.